A helicopter electric drive tail rotor control system and method

Abstract

The invention relates to a control system and method for a helicopter electrically driven tail rotor. The control system includes: pedals, an angular displacement sensor, a helicopter controller, a motor controller, a driver for a tail rotor driving motor, and a motor with a variable pitch structure for the tail rotor Drive, detection unit, gyroscope; motor-reducer integrated structure for driving the tail rotor to rotate, electric drive variable pitch structure. The control method automatically controls the rotation speed of the tail rotor drive motor and adjusts the variable pitch structure according to the change of the pedal angle and the attitude change of the tail of the helicopter detected by the gyroscope, so as to realize the balance or steering of the helicopter. The invention provides a control system and method for a helicopter's electrically driven tail rotor, which replaces the traditional helicopter's internal combustion engine drive and excessive transmission shafts, thereby realizing fast and stable automatic balance and steering of the helicopter, reducing operation difficulty, and enhancing reliability and stability It is beneficial to promote the progress and development of electric helicopter technology.

Description

technical field [0001] The invention relates to the field of helicopter design and control, in particular to a helicopter electric drive tail rotor control system and method. Background technique [0002] The power source of the traditional helicopter tail rotor is generally from the main engine, which is transmitted to the tail rotor through the reducer and the transmission shaft. At present, the helicopter tail rotor is generally composed of intermediate reducer, tail drive shaft, tail reducer, tail rotor pitch change rod and other components, wherein the intermediate reducer, tail drive shaft, and tail reducer transfer the energy from the main reducer to Tail rotor, which drives the tail rotor to rotate; the pilot controls the pedal to drive the tail rotor pitch change rod through the control line, thereby changing the angle of attack of the tail rotor blade and changing the thrust (pull force) of the tail rotor blade to achieve the purpose of helicopter balance or direct...

AI Technical Summary

Problems solved by technology

[0003] The existing helicopter tail rotor system has the characteristics of large structural weight, large energy loss, large vibration and noise, possible jamming of the control rod system, difficulty in assembly and maintenance, etc.

The existing variable pitch structure of helicopters mostly uses a worm gear mechanism to control the movement of the variable pitch ring, and the structure is relatively complicated.

Moreover, in the variable-pitch operation, the helicopter balance and steering are controlled entirely by the driver stepping on the pedals. The driving is difficult and unstable, and it is easy to vibrate.

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